| 摘要 |
The expense of fabricating an annular combustor (10) for a gas turbine is minimized by providing a combustor housing (12) including an axially extending sleeve (14) and an annular liner (18) disposed within the housing (12) and about the sleeve (14). The annular liner (18) has concentric inner and outer axially elongated walls (20, 22) spaced from the sleeve (14) and the housing (12), respectively, and also has a radially extending wall (24) spaced from the housing (12) and interconnecting the inner and outer walls (20, 22) at one end to define a combustion chamber (26). The liner (18) to spaced from the housing (12) the sleeve (14) to define a compressed air flow path (28) extending from a radially outer compressed air inlet (30) to a radially inner compressed air outlet (32) in communication with the combustion chamber (26) axially remote from the radially extending wall (24). The annular combustor (26) is provided with a plurality of fuel injectors (36, 40) for injecting a liquid fuel to be burned into the liner (18) in a generally tangential direction adjacent the radially extending wall (24) to impact liquid fuel directly onto an inner surface (22a) of the outer wall (22) adjacent to the radially extending wall (24). The annular combustor (26) also includes a plurality of open ended elongated tubes (34) in the outer wall (22) intermediate the compressed air inlet (30) and the radially extending wall (24) to direct air for combustion into the combustion chamber (26). With this arrangement, a mixture of fuel and air may be ignited within the combustion chamber (26) and the resulting hot gases of combustion utilized to drive the gas turbine.
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